Separation Control for a Transonic Convex Corner Flow Using Ramp-Type Vortex Generators

A flap can be used to control wing camber and as a high-lift device. A convex corner is a simplified model of the upper surface of a flap. At transonic speeds, shock-induced boundary layer separation (SIBLS) occurs at greater freestream Mach numbers and deflection angles. This results in energy losses and a reduction in aerodynamic performance. This study installs ramp-type vortex generators (VGs) upstream of a convex corner, and the effect of the height of the VG on SIBLS is determined. As the height of the VG increases, the magnitude of the mean surface pressure upstream of the corner increases and downstream expansion decreases, which results in a reduction in lift. A reduction in peak surface pressure fluctuations, the separation length, and the frequency of shock oscillation is also determined. For flow control and lift enhancement, micro-VGs are more effective.

Automated summary

This study investigates the impact of installing VGs upstream of the convex corner on shock-induced boundary layer separation. The findings indicate that increasing the VG height reduces the occurrence of boundary layer separation induced by shock waves but also leads to a decrease in lift.